US7959409B2 - Repaired vane assemblies and methods of repairing vane assemblies - Google Patents

Repaired vane assemblies and methods of repairing vane assemblies Download PDF

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Publication number
US7959409B2
US7959409B2 US11/680,792 US68079207A US7959409B2 US 7959409 B2 US7959409 B2 US 7959409B2 US 68079207 A US68079207 A US 68079207A US 7959409 B2 US7959409 B2 US 7959409B2
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US
United States
Prior art keywords
vane
annular housing
replacement
edge
section
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related, expires
Application number
US11/680,792
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English (en)
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US20080213092A1 (en
Inventor
Wen Guo
William F. Hehmann
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Honeywell International Inc
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Honeywell International Inc
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Publication date
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Priority to US11/680,792 priority Critical patent/US7959409B2/en
Assigned to HONEYWELL INTERNATIONAL, INC. reassignment HONEYWELL INTERNATIONAL, INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HEHMANN, WILLIAM F., GUO, WEN
Priority to EP08102183A priority patent/EP1965023A2/fr
Publication of US20080213092A1 publication Critical patent/US20080213092A1/en
Application granted granted Critical
Publication of US7959409B2 publication Critical patent/US7959409B2/en
Expired - Fee Related legal-status Critical Current
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/005—Repairing methods or devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00—Restoring or reconditioning objects
    • B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
    • B23P6/005—Repairing turbine components, e.g. moving or stationary blades, rotors using only replacement pieces of a particular form
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49718—Repairing
    • Y10T29/49732—Repairing by attaching repair preform, e.g., remaking, restoring, or patching
    • Y10T29/49734—Repairing by attaching repair preform, e.g., remaking, restoring, or patching and removing damaged material
    • Y10T29/49737—Metallurgically attaching preform

Definitions

  • the inventive subject matter relates to vane assemblies and, more particularly, to repaired vane assemblies and methods for repairing vane assemblies.
  • Turbine engines are used as the primary power source for many types of aircraft. Most turbine engines generally follow the same basic power generation procedure. Air is ingested into the fan section of an engine and is directed against at least one set of stationary vanes toward axial and/or radial compressors. The compressed air is mixed with fuel and burned, and the expanding hot combustion gases are directed against another set of stationary vanes in the engine. The vanes deflect the high velocity gas flow so as to impinge on turbine blades mounted on a rotatable turbine disk. The force of the impinging gas causes the turbine disk to spin at high speed to create power.
  • stationary vanes are disposed along one or more sections of the air flow path.
  • the stationary vanes may be part of an assembly, such as an air diffuser assembly or other component, and they typically extend between an outer annular housing and an inner annular housing.
  • the vanes and housings may be integrally cast.
  • the assembly may be made from a superalloy, including, but not limited to, nickel-based, cobalt-based, and iron-based superalloys.
  • integrally cast assemblies offer many advantages, they may have drawbacks.
  • the repair of these assemblies may present challenges. Specifically, foreign objects such as sand, dirt, and other such debris may impinge against a leading edge of a vane and cause damage.
  • the individual vanes are permanently attached to the housings, the damaged vane may not be easily removed for repair.
  • the superalloys from which the assemblies may be made are generally difficult to weld successfully.
  • welding techniques often include heating the assembly to high temperatures, ranging from 1800° F. to 2000° F. (980° C. to 1095° C.), which may cause the vanes or housings to experience distorting and deformation rendering the vane unusable for further engine service.
  • some vanes have complex leading edge geometries thereby making it difficult to deposit filler or cladding material thereon.
  • Braze repair may be another option, however, precision process control may then be needed to prevent distortion of the assembly under braze thermal cycles.
  • a method for repairing a vane assembly is desired that may be used to fully restore the geometry, dimension, and desired properties of degraded vanes. Additionally, it is desirable to repair the vane assembly without causing distortion and/or damage to the vane. Additionally, it is desirable to have a repair method that is less costly as compared to the alternative of replacing worn parts with new ones.
  • the inventive subject matter provides repair methods and repaired vane assemblies.
  • a method for repairing a vane assembly, where the vane assembly includes an inner annular housing, an outer annular housing, and a vane extending therebetween.
  • the method includes removing an identified section of the vane to thereby form a pocket in an inner surface of the outer annular housing, a slot through the inner annular housing, and an edge on the vane, inserting a replacement vane portion through the formed slot such that a first edge of the replacement vane portion is disposed in the pocket and at least a portion of the first edge is spaced apart from at least a portion of the outer annular housing inner surface, and welding a section of the replacement vane portion to the annular inner annular housing.
  • another method includes removing an identified section of the vane to thereby form a pocket in an inner surface of the outer annular housing, a slot through the inner annular housing, and a beveled edge on the vane, inserting a replacement vane portion through the formed slot such that an outer edge of the replacement vane portion is disposed in the pocket and an aft edge of the replacement vane portion is disposed adjacent to and spaced apart from the beveled edge of the vane, the replacement vane portion having a substantially erosion-resistant and oxidation-resistant coating and the aft edge substantially complementing the vane beveled edge, and welding a section of the replacement vane portion to the inner annular housing.
  • a repaired vane assembly in still another embodiment, and by way of example only, includes an outer annular housing, an inner annular housing, and a repaired vane.
  • the outer annular housing has an inner surface and a pocket formed therein.
  • the inner annular housing is disposed proximate the outer annular housing.
  • the repaired vane extends between the outer annular housing and the inner annular housing and includes an original portion and a replacement portion.
  • the original portion is integrally formed with the outer and inner annular housings.
  • the replacement portion includes an outer edge disposed within the outer annular housing pocket and a section welded to the inner annular housing.
  • FIG. 1 is a cross-sectional view of a portion of a vane assembly, according to an embodiment
  • FIG. 2 is a flow diagram of a method of repairing a vane assembly, according to an embodiment
  • FIG. 3 is a cross-sectional view of a vane assembly identifying a section of an original vane to be removed, according to an embodiment
  • FIG. 4 is a cross-sectional view of a vane assembly with the identified section of the original vane removed therefrom, according to an embodiment
  • FIG. 5 is a side view of a replacement vane portion that may be used in the repair method shown in FIG. 2 , according to an embodiment
  • FIG. 6 is a cross-sectional view of the original vane shown in FIG. 4 taken along line 6 - 6 , according to an embodiment
  • FIG. 7 is a cross sectional view of the replacement vane portion shown in FIG. 5 taken along line 7 - 7 , according to an embodiment
  • FIG. 8 is a cross-sectional view of a vane assembly during another step of the repair method shown in FIG. 2 , according to an embodiment.
  • FIG. 9 is a cross-sectional view of a repaired vane taken along line 9 - 9 in FIG. 8 during another step of the repair method shown in FIG. 2 , according to an embodiment.
  • inventive subject matter is merely exemplary in nature and is not intended to limit the inventive subject matter or the application and uses of the inventive subject matter. Additionally, although the inventive subject matter is described as being implemented in the context of an air diffuser assembly, the inventive subject matter may alternatively be implemented as part of any other apparatus having a vane integrally formed between an inner and an outer housing. Furthermore, there is no intention to be bound by any theory presented in the preceding background or the following detailed description.
  • FIG. 1 is a cross-sectional view of a portion of a vane assembly 100 , according to an embodiment.
  • the vane assembly 100 is shown relative to a centerline 101 and may be disposed in an engine (not shown) and used as part of an air diffuser assembly or any component in which air may be directed to flow in a particular direction.
  • the vane assembly 100 includes a plurality of vanes 102 (two of which are illustrated), an outer annular housing 104 , and an inner annular housing 106 .
  • the vanes 102 extend between and may be integrally cast as part of the outer and inner annular housings 104 , 106 .
  • the vanes 102 , outer annular housing 104 , and inner annular housing 106 may be made of a metal alloy, such as, nickel-base superalloy or precipitation stainless steel.
  • Each vane 102 includes a leading edge 108 , a trailing edge 110 , an outer housing edge 112 , and an inner housing edge 114 .
  • FIG. 2 is a flow diagram of a method of repairing the vane assembly 100 , according to an embodiment.
  • the method 200 includes identifying a section of an original vane having a damaged portion thereon, step 202 . Next, the identified section is removed to thereby form a pocket in an inner surface of the outer annular housing 104 and a slot through the inner annular housing 106 , step 204 .
  • a replacement vane portion is inserted through the formed slot such that an edge of the replacement vane portion is disposed in the pocket, step 206 .
  • a section of the replacement vane portion is then welded to the inner annular housing 106 , step 208 .
  • FIG. 3 is a cross-sectional view of the vane assembly 100 identifying a section 300 of the original vane 302 to be removed, according to an embodiment.
  • the identified section 300 includes the damaged portion of the original vane 302 and has an axial length measured from the damaged portion to another part of the original vane 302 .
  • the damaged portion is on the leading edge 108 of the original vane 302 .
  • the identified section 300 of the original vane 302 is then removed such that a pocket 308 is formed in an inner surface 310 of the outer annular housing 104 and a slot 312 is formed through the inner annular housing 106 (step 204 ), as shown in FIG. 4 .
  • the identified section 300 may be removed using a conventional machining process. For example, an electrical discharge machining process may be employed. In an electrical discharge machining process, a wire electrode may be contacted with the original vane 302 and an electrical discharge may be passed therebetween to thereby cut through the original vane 302 .
  • the wire electrode may be a straight wire, or may be shaped substantially similarly to the identified section 300 or to a replacement vane portion 314 (shown in FIG. 5 ).
  • the wire electrode may cut through a portion of the inner annular housing 106 located radially inwardly from the identified section 300 .
  • the cut may form the slot 312 .
  • the slot 312 may have a length and a width that are substantially equal to or greater than the axial length and width of the identified section 300 .
  • the wire electrode may then cut through the original vane 302 to thereby remove the identified section 300 .
  • FIG. 6 is a cross-sectional view of the cut original vane 302 shown in FIG. 4 taken along line 6 - 6 .
  • the identified section 300 may be removed such that a radially extending forward edge 316 is formed on the original vane 302 .
  • the forward edge 316 may be beveled.
  • the forward edge 316 may be beveled at a 45° relative to a surface 303 of the original vane 302 .
  • the forward edge 316 may be beveled at other angles in a range from about 30° to about 60° relative to the surface 303 of the original vane 302 .
  • the wire electrode may then erode a portion of the outer annular housing inner surface 310 to form the pocket 308 .
  • the pocket 308 may have a length that may be equal to or greater than an axial length of the identified section 300 .
  • FIGS. 5 and 7 provide a side view and a cross-sectional view of the replacement vane portion 314 along line 7 - 7 in FIG. 5 , according to an embodiment.
  • the replacement vane portion 314 is shaped similarly to the removed section of the original vane 302 and includes an outer edge 318 , an inner edge 320 , a leading edge 322 , and an aft edge 324 .
  • the aft edge 324 is shaped to substantially complement the shape of the forward edge 316 of the original vane 302 after the damaged section has been removed. In this regard, the aft edge 324 may be beveled to an angle, such as, for example, 45° relative to a side surface 328 .
  • the replacement vane portion 314 may include a coating 326 of a substantially erosion- and/or oxidation-resistant material.
  • the coating 326 may be included on the leading edge 322 and both side surfaces 328 , 329 of the replacement vane portion 314 , while the outer edge 318 , the inner edge 320 , and the aft edge 324 may not be coated.
  • the coating 326 may be made of titanium nitride (TiN).
  • FIG. 8 a cross-sectional view of the vane assembly 100 is shown including the replacement vane portion 314 disposed therein.
  • the replacement vane portion 314 may be disposed within the pocket 308 without being attached to the outer annular housing 104 .
  • the replacement vane portion 314 may be disposed such that at least a portion of the outer edge 318 may be sufficiently spaced apart from the outer annular housing inner surface 310 to thereby form a gap 330 therebetween.
  • the gap 330 may be configured to accommodate radial expansion that may occur when the replacement vane portion 314 is exposed to a sufficiently high temperature.
  • FIG. 9 is a cross-sectional view of the replacement vane portion 314 and original vane 302 taken along line 9 - 9 , according to an embodiment.
  • the aft edge 324 of the replacement vane portion 314 and the forward edge 316 of the original vane 302 are spaced apart to form a gap 332 therebetween.
  • the gap 332 may be included to provide minimal flow disruption of air traveling across the surfaces of the replacement vane portion 314 and the original vane 302 .
  • a section of the replacement vane portion 314 is then welded to the annular inner housing 106 , step 208 .
  • the second section may include the inner edge 320 or a portion of the replacement vane portion 314 that is proximate the inner edge 320 .
  • the second section and inner annular housing 106 are laser welded together.
  • the second section and inner annular housing 106 may be welded together using a conventional hand-held laser weld apparatus.
  • the second section and inner annular housing 106 may be welded using a tungsten inert gas welding process, or some other welding process.
  • a method has now been provided that may be used to repair integrally formed vane assemblies.
  • the method may be simple and inexpensive to perform may be used to fully restore geometry, dimension and desired properties of degraded vanes. Additionally, the method may allow control of welding parameters so that assembly repairs may be affected without distortion and damage to the vane. Moreover, the method may be less costly as compared to the alternative of replacing a damaged vane assembly with a new assembly.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US11/680,792 2007-03-01 2007-03-01 Repaired vane assemblies and methods of repairing vane assemblies Expired - Fee Related US7959409B2 (en)

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US11/680,792 US7959409B2 (en) 2007-03-01 2007-03-01 Repaired vane assemblies and methods of repairing vane assemblies
EP08102183A EP1965023A2 (fr) 2007-03-01 2008-02-29 Ensembles d'aubes réparés et procédés pour réparer des ensembles d'aubes

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US11/680,792 US7959409B2 (en) 2007-03-01 2007-03-01 Repaired vane assemblies and methods of repairing vane assemblies

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US20160069185A1 (en) * 2013-03-19 2016-03-10 Alstom Technology Ltd Method for reconditioning a hot gas path part of a gas turbine
US9627500B2 (en) 2015-01-29 2017-04-18 Samsung Electronics Co., Ltd. Semiconductor device having work-function metal and method of forming the same
US9828867B2 (en) 2012-12-29 2017-11-28 United Technologies Corporation Bumper for seals in a turbine exhaust case
US9845695B2 (en) 2012-12-29 2017-12-19 United Technologies Corporation Gas turbine seal assembly and seal support
US9850774B2 (en) 2012-12-29 2017-12-26 United Technologies Corporation Flow diverter element and assembly
US9890663B2 (en) 2012-12-31 2018-02-13 United Technologies Corporation Turbine exhaust case multi-piece frame
US9903224B2 (en) 2012-12-29 2018-02-27 United Technologies Corporation Scupper channelling in gas turbine modules
US9903216B2 (en) 2012-12-29 2018-02-27 United Technologies Corporation Gas turbine seal assembly and seal support
US9982561B2 (en) 2012-12-29 2018-05-29 United Technologies Corporation Heat shield for cooling a strut
US9982564B2 (en) 2012-12-29 2018-05-29 United Technologies Corporation Turbine frame assembly and method of designing turbine frame assembly
US10006306B2 (en) 2012-12-29 2018-06-26 United Technologies Corporation Turbine exhaust case architecture
US10054009B2 (en) 2012-12-31 2018-08-21 United Technologies Corporation Turbine exhaust case multi-piece frame
US10053998B2 (en) 2012-12-29 2018-08-21 United Technologies Corporation Multi-purpose gas turbine seal support and assembly
US10060279B2 (en) 2012-12-29 2018-08-28 United Technologies Corporation Seal support disk and assembly
US10087843B2 (en) 2012-12-29 2018-10-02 United Technologies Corporation Mount with deflectable tabs
US10138742B2 (en) 2012-12-29 2018-11-27 United Technologies Corporation Multi-ply finger seal
US10240481B2 (en) 2012-12-29 2019-03-26 United Technologies Corporation Angled cut to direct radiative heat load
US10240532B2 (en) 2012-12-29 2019-03-26 United Technologies Corporation Frame junction cooling holes
US10294819B2 (en) 2012-12-29 2019-05-21 United Technologies Corporation Multi-piece heat shield
US10329957B2 (en) 2012-12-31 2019-06-25 United Technologies Corporation Turbine exhaust case multi-piece framed
US10329956B2 (en) 2012-12-29 2019-06-25 United Technologies Corporation Multi-function boss for a turbine exhaust case
US10330011B2 (en) 2013-03-11 2019-06-25 United Technologies Corporation Bench aft sub-assembly for turbine exhaust case fairing
US10378370B2 (en) 2012-12-29 2019-08-13 United Technologies Corporation Mechanical linkage for segmented heat shield
US10472987B2 (en) 2012-12-29 2019-11-12 United Technologies Corporation Heat shield for a casing

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US8839625B2 (en) * 2010-06-08 2014-09-23 Hamilton Sunstrand Corporation Gas turbine engine diffuser having air flow channels with varying widths
US8770933B2 (en) * 2010-09-10 2014-07-08 Honeywell International Inc. Turbine nozzle assemblies and methods for repairing turbine nozzle assemblies
US9227277B2 (en) * 2012-08-10 2016-01-05 General Electric Company Method for repairing a turbine diaphragm and diaphragm assembly resulting therefrom

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US10006306B2 (en) 2012-12-29 2018-06-26 United Technologies Corporation Turbine exhaust case architecture
US10087843B2 (en) 2012-12-29 2018-10-02 United Technologies Corporation Mount with deflectable tabs
US9845695B2 (en) 2012-12-29 2017-12-19 United Technologies Corporation Gas turbine seal assembly and seal support
US9850774B2 (en) 2012-12-29 2017-12-26 United Technologies Corporation Flow diverter element and assembly
US10329956B2 (en) 2012-12-29 2019-06-25 United Technologies Corporation Multi-function boss for a turbine exhaust case
US9903224B2 (en) 2012-12-29 2018-02-27 United Technologies Corporation Scupper channelling in gas turbine modules
US9903216B2 (en) 2012-12-29 2018-02-27 United Technologies Corporation Gas turbine seal assembly and seal support
US10138742B2 (en) 2012-12-29 2018-11-27 United Technologies Corporation Multi-ply finger seal
US9982561B2 (en) 2012-12-29 2018-05-29 United Technologies Corporation Heat shield for cooling a strut
US9982564B2 (en) 2012-12-29 2018-05-29 United Technologies Corporation Turbine frame assembly and method of designing turbine frame assembly
US10378370B2 (en) 2012-12-29 2019-08-13 United Technologies Corporation Mechanical linkage for segmented heat shield
US10294819B2 (en) 2012-12-29 2019-05-21 United Technologies Corporation Multi-piece heat shield
US10053998B2 (en) 2012-12-29 2018-08-21 United Technologies Corporation Multi-purpose gas turbine seal support and assembly
US9828867B2 (en) 2012-12-29 2017-11-28 United Technologies Corporation Bumper for seals in a turbine exhaust case
US10941674B2 (en) 2012-12-29 2021-03-09 Raytheon Technologies Corporation Multi-piece heat shield
US10472987B2 (en) 2012-12-29 2019-11-12 United Technologies Corporation Heat shield for a casing
US10240481B2 (en) 2012-12-29 2019-03-26 United Technologies Corporation Angled cut to direct radiative heat load
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